The present invention concerns a method of utilising the waste heat contained in the exhaust gas of an internal combustion engine, comprising a turbine (20). To provide an apparatus and a method of operating same which directly supplies additional drive energy which otherwise would be lost as waste heat, it is proposed according to the invention that the turbine is an inverse turbine connected downstream of the exhaust gas outlet of the internal combustion engine and comprising at the inlet side an expansion stage (23) and at the outlet side a subsequent compressor (21), wherein the expansion stage and the compressor of the inverse turbine are so designed that the downstream-disposed compressor of the inverse turbine generates at the outlet of the expansion stage (23) a reduced pressure (p1) below the ambient pressure (p0), wherein the outlet (2b) of the compressor (21) is at the level of the ambient pressure and the compressor of the inverse turbine is driven by the turbine.

The present invention is a system, method and computer program for operating a land-or marine-based multi-spool gas turbine system for generating electrical power to supply a load, wherein the system comprises a multi-spool gas turbine engine, and the method comprises controlling the rotational speeds of the at least two generators independently of each other so as to directly control the rotational speeds of the shafts of the spools, the at last two generators being operable to generate electrical current to supply the load, and regulating the amount of heat generated the first heat generating equipment. A computer program to perform the method is also disclosed.

A method of generating electric power includes expanding a flow of exhaust gas from a combustion process as the exhaust gas passes through a turbo-expander disposed on a turbo-crankshaft. The flow of exhaust gas from the turbo-expander is routed through an absorber section of an open cycle absorption chiller system. Water from the exhaust gas is absorbed via a first refrigerant solution disposed in the absorber section as the exhaust gas passes through the first refrigerant solution and out of the absorber section. The flow of exhaust gas from the absorber section is compressed as the exhaust gas passes through a turbo-compressor disposed on the turbo-crankshaft. Electrical power is generated from a bottoming cycle generator disposed on the turbo-crankshaft.

A bottoming cycle power system includes a turbine generator and an open cycle absorption system. The turbine-generator includes a turbo-expander and turbo-compressor disposed on a turbo-crankshaft. The turbo-expander is operable to rotate the turbo-crankshaft as a flow of exhaust gas from a combustion process passes through the turbo-expander. The turbo-compressor is operable to compress the flow of exhaust gas after the exhaust gas passes through the turbo-expander. The open cycle absorption chiller system includes an absorber section that is operable to receive the flow of exhaust gas from the turbo-expander. The absorber section includes a first refrigerant solution that is operable to absorb water from the exhaust gas as the exhaust gas passes through the first refrigerant solution. The absorber section is also operable to route the flow of exhaust gas to the turbo-compressor after the flow of exhaust gas has passed through the first refrigerant solution.

Aircraft engines include a turbine engine comprising a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the burner section passes through the turbine section, a condensing assembly arranged downstream of the turbine section of the turbine engine along the core flow path, and an exhaust compressor arranged downstream of the condensing assembly along the core flow path. The condensing assembly is configured to reduce a mass flow of the exhaust compressor by condensing water vapor from the core flow and removing liquid water from the core flow.

An engine system includes a turbine engine including a compressor section, a combustor section having a burner, a turbine section, and a nozzle in an open-loop configuration. The engine system also includes a bottom-cycle apparatus and an exhaust heat exchanger downstream of the turbine section of the turbine engine configured to reject heat from the turbine engine to the bottoming-cycle apparatus and create a cooled turbine exhaust in the turbine engine. The engine system further includes an exhaust compressor arranged downstream of the exhaust heat exchanger and upstream of the nozzle of the turbine engine configured to compress the cooled turbine exhaust stream and increase a pressure of the cooled turbine exhaust stream prior to exiting the nozzle of the turbine engine.

A bottoming cycle power system includes a turbo-expander operable to rotate a turbo-crankshaft as a flow of exhaust gas from a combustion process passes through the turbo-expander. A turbo-compressor is operable to compress the flow of exhaust gas after the exhaust gas passes through the turbo-expander. An open cycle absorption chiller system includes an absorber section operable to receive the flow of exhaust gas from the turbo-expander and to mix the flow of exhaust gas with a first refrigerant solution within the absorber section. The first refrigerant solution is operable to absorb water from the exhaust gas as the exhaust gas passes through the first refrigerant solution. The absorber section is operable to route the flow of exhaust gas to the turbo-compressor after the flow of exhaust gas has passed through the first refrigerant solution.

Aircraft engines include a turbine engine comprising a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the burner section passes through the turbine section, a condensing assembly arranged downstream of the turbine section of the turbine engine along the core flow path, and an exhaust compressor arranged downstream of the condensing assembly along the core flow path. The condensing assembly is configured to reduce a mass flow of the exhaust compressor by condensing water vapor from the core flow and removing liquid water from the core flow.

A bottoming cycle power system includes a turbo-expander operable to rotate a turbo-crankshaft as a flow of exhaust gas from a combustion process passes through the turbo-expander. A turbo-compressor is operable to compress the flow of exhaust gas after the exhaust gas passes through the turbo-expander. An open cycle absorption chiller system includes an absorber section operable to receive the flow of exhaust gas from the turbo-expander and to mix the flow of exhaust gas with a first refrigerant solution within the absorber section. The first refrigerant solution is operable to absorb water from the exhaust gas as the exhaust gas passes through the first refrigerant solution. The absorber section is operable to route the flow of exhaust gas to the turbo-compressor after the flow of exhaust gas has passed through the first refrigerant solution.

A regenerative heat engine may include a first compressor configured to compress an air stream, a regenerator configured to preheat a compressed air stream received from the first compressor, a combustion system configured to generate a combustion gas stream by igniting a mixture of the preheated compressed air stream from the regenerator and a pressurized fuel stream, a flow control mechanism configured to divide the combustion gas stream received from the combustion system into a first combustion gas stream and a second combustion gas stream, a first turbine configured to receive the first combustion gas stream and drive the first compressor, where a first exhaust stream from the first turbine fed into the regenerator, a second compressor, a second turbine configured to receive the second combustion gas stream and drive the second compressor, a heat exchanger configured to receive a second exhaust stream from the second turbine and cool the second exhaust stream, and an external load coupled with the second turbine.